JP2977389B2 - Gas turbine hot parts coatings - Google Patents
Gas turbine hot parts coatingsInfo
- Publication number
- JP2977389B2 JP2977389B2 JP4258053A JP25805392A JP2977389B2 JP 2977389 B2 JP2977389 B2 JP 2977389B2 JP 4258053 A JP4258053 A JP 4258053A JP 25805392 A JP25805392 A JP 25805392A JP 2977389 B2 JP2977389 B2 JP 2977389B2
- Authority
- JP
- Japan
- Prior art keywords
- gas turbine
- hot parts
- hardness
- turbine hot
- coating
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
- Coating By Spraying Or Casting (AREA)
Description
【０００１】[0001]
【産業上の利用分野】本発明はガスタービン燃焼器及び
尾筒の内面、ガスタービン動静翼の内外シュラウト等の
ガスタービン高温部品の耐食性及び耐酸化性を向上する
ためのプラズマ溶射被覆材に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a plasma spray coating for improving the corrosion resistance and oxidation resistance of high-temperature components of gas turbines, such as the inner surfaces of gas turbine combustors and transition pieces, and inner and outer shrouds of gas turbine moving and stationary blades.
【０００２】[0002]
【従来の技術】ガスタービンでは例えば動静翼の耐食
性、耐酸化性及び耐熱性を向上するために、翼表面に金
属又は金属化合物の微粉末やサーメットなどの高融点材
料を、プラズマジェットを使って表面被覆するプラズマ
溶射が行われている。2. Description of the Related Art In a gas turbine, for example, in order to improve the corrosion resistance, oxidation resistance and heat resistance of the moving and stationary blades, a high melting point material such as a fine powder of metal or a metal compound or cermet is applied to the blade surface by using a plasma jet. Plasma spraying for surface coating is performed.
【０００３】従来技術でのプラズマ溶射に使われている
金属粉末の化学組成はＣｏ，Ｎｉ，Ｃｒを主成分とし、
ＡｌとＹを加えたもので、コーティング手法としては減
圧プラズマ溶射法が使われている。その化学組成の一例
をあげると、重量％でＮｉ：３２％、Ｃｒ：２２％、Ａ
ｌ：８％、Ｙ：０．５％、Ｃｏ：残部である。The chemical composition of a metal powder used for plasma spraying in the prior art is mainly composed of Co, Ni, and Cr.
A reduced pressure plasma spraying method is used as a coating technique by adding Al and Y. As an example of the chemical composition, Ni: 32%, Cr: 22%, A
l: 8%, Y: 0.5%, Co: balance.
【０００４】[0004]
【発明が解決しようとする課題】前記従来の技術には下
記の問題点があった。 （１）コーティング層の硬度が比較的に低い。またこの
硬度はガスタービンの運転時間と曝された温度によって
逐次低下していく。 （２）このため、燃料中に硬質微粉が混入したり（高炉
ガス中の酸化鉄等）、吸入大気中のけい砂等の影響によ
って、コーティング層が侵食されて摩耗し、翼の耐食、
耐熱、耐酸化性が低下する場合があった。The above prior art has the following problems. (1) The hardness of the coating layer is relatively low. The hardness gradually decreases depending on the operation time of the gas turbine and the temperature to which the gas turbine is exposed. (2) For this reason, hard fine powder is mixed in the fuel (iron oxide in the blast furnace gas, etc.), and the coating layer is eroded and worn by the influence of silica sand in the intake air, and the corrosion resistance of the blade is reduced.
Heat resistance and oxidation resistance were sometimes reduced.
【０００５】本発明は上記技術水準に鑑み、コーティン
グ層の硬度が加熱前と加熱後ともに著しく向上し、燃焼
ガス中の硬質異物が衝突しても侵食されず、被覆材が摩
耗したり剥離しないガスタービン高温部品のプラズマ溶
射用被覆材を提供しようとするものである。In the present invention, in view of the above technical level, the hardness of the coating layer is remarkably improved both before and after heating, so that the hard material in the combustion gas is not eroded by collision, and the coating material is not worn or peeled. An object of the present invention is to provide a coating material for plasma spraying a high temperature component of a gas turbine.
【０００６】[0006]
【課題を解決するための手段】本発明は化学組成が重量
比で、Ｃｒ：２２〜２４％、Ａｌ：８．５〜９．５％、
Ｗ：９〜１１％、Ｙ：０．３〜０．７％、Ｃ：０．７〜
１．２％、Ｃｏ：残よりなることを特徴とするガスター
ビン高温部品のプラズマ溶射用被覆材である。According to the present invention, the chemical composition is, by weight, 22 to 24% of Cr, 8.5 to 9.5% of Al,
W: 9 to 11%, Y: 0.3 to 0.7%, C: 0.7 to
1.2%, Co: a coating material for plasma spraying of high temperature components of gas turbines, characterized by being composed of the balance.
【０００７】[0007]
【作用】本発明のガスタービン高温部品の被覆材によれ
ば、コーティング層の硬度が加熱前及び加熱後ともに著
しく向上し、燃焼ガス中の硬質異物が衝突しても侵食さ
れず、被覆層が摩耗したり剥離しない。According to the coating material for a gas turbine high-temperature component of the present invention, the hardness of the coating layer is remarkably improved both before and after heating. Does not wear or peel.
【０００８】[0008]
【実施例】本発明の被覆材の化学組成は重量比で、Ｃ
ｒ：２２〜２４％、Ａｌ：８．５〜９．５％、Ｗ：９〜
１１％、Ｙ：０．３〜０．７％、Ｃ：０．７〜１．２
％、Ｃｏ：残よりなるもので、これを従来技術の被覆材
（重量％で、Ｎｉ：３２％、Ｃｒ：２２％、Ａｌ：８
％、Ｙ：０．５％、Ｃｏ：残）と対比した実験結果を図
１に示す。いずれも加熱前と８５０℃、９００℃、９５
０℃で３０００時間（１２５日間）曝されたのちでのビ
ッカース硬度を示す。硬度は４箇所での平均を示す。加
熱前後ともにコーティング層表面硬度は約１．５倍に向
上している。EXAMPLES The chemical composition of the coating material of the present invention is expressed in terms of
r: 22 to 24%, Al: 8.5 to 9.5%, W: 9 to
11%, Y: 0.3-0.7%, C: 0.7-1.2
%, Co: residue, which is a coating material of the prior art (in terms of% by weight, Ni: 32%, Cr: 22%, Al: 8).
%, Y: 0.5%, Co: residual) are shown in FIG. Before heating, 850 ° C, 900 ° C, 95%
The Vickers hardness after exposure for 3000 hours (125 days) at 0 ° C. is shown. The hardness indicates an average at four points. Both before and after heating, the surface hardness of the coating layer is improved by about 1.5 times.
【０００９】[0009]
【発明の効果】本発明によれば、ガスタービン高温部品
のプラズマ溶射層の硬度が上昇し、燃焼ガス中の硬質異
物によって溶射被膜が損傷されない。従って翼の耐食、
耐酸化、耐熱性の低下によって翼寿命が短縮されず、ガ
スタービン信頼性が向上する。According to the present invention, the hardness of the plasma sprayed layer of the gas turbine high-temperature component is increased, and the sprayed coating is not damaged by hard foreign matters in the combustion gas. Therefore the wing corrosion resistance,
The blade life is not shortened due to the decrease in oxidation resistance and heat resistance, and the reliability of the gas turbine is improved.
【図１】本発明の被覆材によってガスタービン高温部品
を被覆したコーティング層の硬さと従来の被覆材によっ
て同じく被覆したコーティング層のビッカース硬度を比
較した図表。FIG. 1 is a chart comparing the hardness of a coating layer coated on a gas turbine high-temperature component with the coating material of the present invention and the Vickers hardness of a coating layer coated similarly with a conventional coating material.
Claims (1)
％、Ａｌ：８．５〜９．５％、Ｗ：９〜１１％、Ｙ：
０．３〜０．７％、Ｃ：０．７〜１．２％、Ｃｏ：残よ
りなることを特徴とするガスタービン高温部品のプラズ
マ溶射用被覆材。1. The chemical composition has a weight ratio of Cr: 22 to 24.
%, Al: 8.5 to 9.5%, W: 9 to 11%, Y:
A coating material for plasma spraying a high temperature component of a gas turbine, comprising 0.3 to 0.7%, C: 0.7 to 1.2%, and Co: residue.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4258053A JP2977389B2 (en) | 1992-09-28 | 1992-09-28 | Gas turbine hot parts coatings |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4258053A JP2977389B2 (en) | 1992-09-28 | 1992-09-28 | Gas turbine hot parts coatings |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH06108222A JPH06108222A (en) | 1994-04-19 |
| JP2977389B2 true JP2977389B2 (en) | 1999-11-15 |
Family
ID=17314888
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP4258053A Expired - Fee Related JP2977389B2 (en) | 1992-09-28 | 1992-09-28 | Gas turbine hot parts coatings |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2977389B2 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP6550227B2 (en) * | 2014-10-31 | 2019-07-24 | トーカロ株式会社 | Thermal spray powder, method of producing thermal spray coating, thermal spray coating, and roll |
-
1992
- 1992-09-28 JP JP4258053A patent/JP2977389B2/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| JPH06108222A (en) | 1994-04-19 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 19990817 |
|
| LAPS | Cancellation because of no payment of annual fees |